Load stabilizer



sept. 2o, 1960 w; w. LYSAK LOAD STABILIZER Filed March l?, 1958 2sheets-snee; 1

I "il u QQ j( l Sept. 20, 1960 ww, LYSAK 2,953,330

LOAD STABILIZER Filed March 17. 1958 2 Sheets-Sheetv 2 /NVEN TOR WAL TERW LVSAK LOAD STABILIZER Walter W. Lysak, Trumbull, Conn., assignor toUnited Aircraft Corporation, East Hartford, Conn., a corporation ofDelaware Filed Mar. 17, 1958, Ser. No. 721,721

9 Claims. (Cl. 244-118) ThisV invention relates to means for stabilizingloads being lifted, carried, or lowered by aircraft, especiallyhelicopters. f

It is an object of this invention to provide means for carrying loadsbeneath helicopters in which said loads are stabilized to preventoscillations which in many instances lead to serious control problems.

Another object of this device is to provide a stabilizing support on oneside of a location where a load lifting or holding force is beingapplied. Y

A further object of this device is to provide an extension from anaircraft which will engage a load being handled by said aircraft torender said load stable.

Another'object of this invention is to provide an extending member forstabilizing `a load which is retractable.

A further object of this device is to provide adjustable means foreasily accepting loads of varying widths.

Another object of this invention is to provide a device having controlseasily operated by a pilot to Vachieve maximum handling eihciency.

A further object of this invention is to provide means for stabilizingexternal loads being supported at a single point.

'Ihese and other objects of this invention will become readily apparentfrom the following detailed description of the drawings: f

Fig. 1 is a side View of a helicopter having a load suspended therefromand stabilized by .the invention,

Fig. 2 is an enlarged View of the invention showing the controls and aportion of a load, v

Fig. 3 is a front view of the invention .as shown in Fig. 2 showing asmall portion of the helicopter with a load in place.

Referring to Fig. l, a helicopter is shown having an extended fuselage10, a single main sustaining rotor 12 and a torque compensating rotor 14mounted on an upwardly extending pylon 16. Both rotors are driven by anengine mounted in the nose of the fuselage. A landing gear includes twomain forward wheels 18. Each wheel is connected to the fuselage by -aleg 19 through a bracket 112.

The load stabilizing means 20 is used in conjunction with a load holdingmeans 2.2. The load holding means is of a type generally used forsimilar lifting tasks. It is comprised primarily of four main pants.They are the following: (l) cargo release hook means 24, (2) hook cablesupporting means 26, (3) emergency pilot manual release means 28, and(4) normal pilot release control means 30.

The cargo release hook means 24 includes a housing 32 having a hook 34extending from the bottom thereon being pivoted at 36 and having itshook end extending into the housing 32 where it is engaged by a holdingmechanism. This hook 24 is maintained in place by two sets of cables 38and 40, one set extending from each side of the fuselage of saidhelicopter `10. These cables are attached to the helicopter by brackets42`and aient Ice Patented sept. zo, 1960 are attached to the housing 32of the cargo release hook 24 by pivoted connector members 44.

An emergency release 28 is provided on the cargo release hook means 24for the hook holding mechanism which is operated by a cable 46 connectedto a pilot foot lever 48 by a bell crank 50. The holding mechanism 1sheld in its holding position againstV release by the emergency manualcontrol by a spring 52 which is positioned between a member 54 on thehelicopter and a flange 56 on the foot lever 48. A section of thehelicopter oor is shown at 57.

The cargo release hook means 24 is also provided with a normal' releasewhich is electrically operated and can release the hook holdingmechanism in 'flight or on the ground by means of the electrical conduit58 and electrical switch 60 which is in turn connected to an electricalsource. Switch 60 can be located either on a panel or operating controlstick of the helicopter.

Hook means 24 is also provided with a manually operable ground'operating handle 62 for operating the hook holding mechanism from aposition under the helicopter. An automatic release is also providedwhich will release the holding mechanism and discharge cargo from saidhook means 24 upon contact of the cargo with the gnound.

The load stabilizing means 20 is comprised primarily of four main parts.They are the following: (1) a cargo stabilizing arm 64, (2) armsupporting means 66, (3) varm actuating means 68, and (4) actuatingcontrol means 70.

The cargo stabilizing arm 64 (shown from the front Vin Fig. 3) comprisesa mainr tubular member 72 supported for rotation in arm support means 66in a manner to be hereinafter described. Tubular member 72 has a sleeve74 fixed to each end thereof by means of pins 76 set at night angles toeach other. Extending from each sleeve 74 at 90 to the axis of member 72is a tubular arm member 78. Arm members 78 are parallel to each otherand .each is Welded to its respective sleeve 74. For additional supportareinforcing strip 80 is attached to each sleeve 74 and vthe adjacent endof ann member 78.

On the free end of each tubular arm member 78, a sleeve 82 is aflixedthereto in a manner similar to sleeve 74. Each sleeve 82 is welded toits respective arm 78 and a reinforcing strip is used to insure a rigidconnection. A load bearing tubular member 84 extends between the freeends of tubular arm member 78 and has one of its free ends fixed in eachof the sleeves 82, respectively.. Each end of load bearing tubularmember .84 is pinned -in its respective sleeve 82 by pins 86.Reinforcing arm members 88 extend between each corner where a sleeve 74meets its respective tubular arm member 78, to the -center of the loadbearing tubular member 84. A bracket 90 is provided at each connectionof sleeve 74 to arm 78 and a bracket 92 is provided at the center vofmember 84. f

Slidably mounted on load bearing .tubular member 84 are two sleeves 94each with a load guiding and positioning projection 96 extendingtherefrom. A set screw 9.8 is provided in each sleeve 94 to lixedlyposition it on load bearing tubular member 84. It can be seen that theseprojections can be Slidably moved between a center position to aposition where the sleeves 94 abut their respective end sleeves 82.

Arm supporting means 66 are provided for rotatably supporting the cargostabilizing arm 64,. Supporting means 66 comprises two bearing sleeves100 positioned around tubular member 72, one at each .end thereofadjacent a sleeve 74. Each sleeve 100 is xed to the helicopter structureby a Vlink 102 and a link 104. One .end of .each linky 102 and 104 isfixed Lto a bracket 106 `on its respective sleeve 100. The other end ofeach arm 3 102 is pinned to a bifurcated bracket 108 fixed to the bottomof the ship and the other end of arm 104 is pinned to a bifurcatedbracket 110 xed to the bottom of the main landing gear leg pivot bracket112. The axes of these mounting pins are located at 90 to each other.

Each bearing sleeve 100 is additionally supported in place by two cables114 and 116 extending from the side of the fuselage of said helicopter10, on which the bearing sleeve is located, to a rib located on thesleeve 100. Each cable 114 is attached to the helicopter by a bracket118 and is attached at its other end to a rib on its cooperating sleeve100. Each cable 116 is attached to the helicopter by a bracket 120 andis attached at its other end to a rib on its cooperating sleeve 100.

Arm 64 is rotatable between a position extending downwardly, as shown insolid lines in Fig. 2, and a retracted position extending rearwardly, asshown in dotted lines in the same Fig. 2. The arm actuating means 68comprises a bifurcated lever 122 which extends from the tubular member72 and is fixed thereto through a sleeve member 124. The lever 122 isfixed to the sleeve 124 which is in turn fixed to the tubular member 72.The free end of lever 122 is attached to one end of a linear actuator125 at 126 by a pinned connection. The other end of the linear actuatoris connected to a bifurcated bracket 128 on the helicopter by a pinnedconnection at 130. Linear actuator 125 is moved between its extended andretracted position by an electric motor 132. This motor 132 can beoperated by the pilot through control means including electrical conduit134 and electrical switch 136 which is in turn connected to anelectrical source. While a linear actuator has been shown which iselectrically operated, it is to be understood that other actuators canbe used, such as hydraulic piston and cylinder units.

Operation When it is desired to carry a load by a helicopter in whichstabilization is desired, a rope, chain or cable 140 can be fixedlyattached to the device to be loaded, such as a pole shown in the gures,at a point spaced from the center of gravity of the load. This cable orattaching means can then be connected to the cargo release hook means 24through the use of the hook 34 using the manually operable groundoperating handle 62. The helicopter can then be own in a verticaldirection upwardly until there is sufficient room for the cargostabilizing arm to be positioned in its extended position. When thisaltitude has been reached, the pilot merely operates his electricalswitch 136 to actuate the linear actuator 125. The projections 96 arepositioned on each side of the load to prevent a swingingmotionv aboutits supporting point. The load may now be own to any desired pointwithout fear of any unwanted control problems due to load changes andmovements. The load may now be disposed of by any of the ways provided.That is, the pilot may find it necessary to depress his emergencyrelease foot lever 48 to release the hook 34 and thereby drop the load.However, in normal release the pilot may operate his electrical switchto release the hook 34 or he may set an automatic release so that thecargo will be discharged from the hook means upon contact of the cargowith the ground. A fourth means of releasing the load is to lower thehelicopter to a position which will make the hook means 34 accessible toa person below the ship so that the ground operating handle 62 isavailable for releasing the hook 34.

A load may also be picked up by flying the helicopter downwardly overthe load with the cargo stabilizing arm in its extended position andpositioning it over the load. The -load can then be connected to thecargo -hook release means and the stabilizing arm can be placed in itsproper position. The helicopter then is merely own upwardly. Release ofthe load may be carried out by any of the means set forth above.

It is to be understood that the invention is not limited to the specificembodiment herein illustrated and described, but may be used in other-ways without departure from its spirit as defined by the followingclaims.

I claim:

l. In combination, a helicopter; a load; first load supporting meansextending from said helicopter; said first means pivotally supportingsaid load at a location spaced from the center of gravity of said load;second load stabilizing means comprising an arm extending downwardlyfrom said helicopter engaging said load at a second point spaced fromthe first point; said arm having a first member rotatably mounted onsaid helicopter, arm means extending at an angle from said first member,and a second load contacting member fixed to the arm means and spacedfrom said first member.

2. In combination, a helicopter; means connected to said helicopter forpivotally supporting a load; load stabilizing means for engaging a loadcomprising an arm extending downwardly from said helicopter; said armhaving a first member rotatably mounted on said helicopter, arm meansextending at an angle from said first member, and a second load bearingmember fixed to the arm means and spaced from said first member; meansfor moving said arm on said rotatable member between an extended andretracted position; said last named means including a leverextendingfrom said first member; and actuating means xed to the free endof said lever and said helicopter for rotating said first member.

3. In combination, a helicopter; means connected to said helicopter forpivotally supporting a load; load stabilizing means for engaging a loadcomprising an arm extending downwardly from said helicopter; said armhaving a first member rotatably mounted on said helicopter, arm meansextending at an angle from said first member, and a second load bearingmember fixed to the arm means and spaced from said first member; meansfor moving said arm on said rotatable member between an extended andretracted position; said last named means including a lever extendingfrom said first member; and actuating means for rotating said firstmember; said actuating means comprising a linear actuator having one endattached to the free end of said lever and the other end attached to thehelicopter.

4. In combination, a helicopter; means connected to said helicopter forpivotally supporting a load; load stabilizing means for engaging a `loadcomprising arm means extending downwardly from said helicopter; said armmeans having a first member; said first member having a section with acylindrical surface at each end; a sleeve positioned around eachcylindrical surface; said member being rotatably mounted in saidsleeves; said sleeves being mounted below said helicopter; said armmeans having arms extending at an angle from said first member; a secondload bearing member fixed to the arms and spaced from said first member;and means for moving said arm means on said rotatable member between anextended and retracted position.

5. In combination, a helicopter; means connected to said helicopter forpivotally supporting a load; load stabilizing means for engaging a loadcomprising arm means extending downwardly from said helicopter; said armmeans having a first member; said first member having a section with acylindrical surface at each end; a sleeve positioned around eachcylindrical surface; said member being rotatably mounted in saidsleeves; said sleeves being mounted below said helicopter; said armmeans having arms extending at an `angle from said first member; asecond load bearing member fixed to the arms and spaced from said firstmember; means for moving said arm means on said rotatable member betweenan extended and retracted position, said last named means including alever extending from said first member; and actuating means fixed to thefree end of said lever and said helicopter for rotating said member. Y

6. In combination, a helicopter; means connected to said helicopter forpivotally supporting a load; load stabilizing means for engaging a loadcomprising arm means extending downwardly from said helicopter; said armmeans having a first member; said first member having a section with yacylindrical surface Iat each end; a sleeve positioned around eachcylindrical surface; said member being rotatably mounted in saidsleeves; said sleeves being mounted below said helicopter; said armmeans having arms extending -at an angle from said irst member; a secondload bearing member xed to the arms and spaced from said rst member;means for moving said arm means on said rotatable member between anextended and retracted position, said last named means including a leverextending from said first member, and actuating means for rotating saidlirst member, said actuating means comprising a linear actuator havingone end attached to the free end of said lever and the other endattached to the helicopter.

7. In combination, a helicopter; means connected to4 said helicopter forpivotally supporting a load; load stabilizing means for engaging a loadcomprising an arm extending downwardly from said helicopter; said armhaving a first member rotatably mounted on said helicopter, arm meansextending at an angle from said lirst member, and a second loadpositioning member xed to the arm means and spaced from said rst member;said second load positioning member having two projections for engagingthe sides of a load; means for moving said arm on said rotatable memberbetween an extended and retracted position; said last named meansincluding a lever extending from said first member; and actuating meansxed to the free end of said lever for rotating said rst member.

8. In combination, a helicopter; means connected to said helicopter forpivotally supporting a load; load stabilizing means for engaging a loadcomprising an arm extending downwardly from said helicopter; said armhaving a iirst member rotatably mounted on said helicopter, yarm meansextending at an angle from said first member, and a second loadpositioning member lixed to the arm means and spaced from said rstmember; said second load positioning member having two projections forengaging the sides of a load; means for moving said yarm on saidrotatable member between an extended and retracted position; said lastnamed means including a lever extending from said rst member; andactuating means fixed to the free end of said lever for rotating saidtirst member, said actuating means comprising a linear actuator havingone end attached to the free end of said lever and the other endattached to the helicopter.

9. In combination, a helicopter; means connected to said helicopter forpivotally supporting a load; load stabilizing means for engaging a loadcomprising an arm extending downwardly from said helicopter; said armhaving a lrst member rotatably mounted on said helicopter, arm meansextending at an angle from said rst member, and a second loadpositioning member lixed to the arm means and spaced from said rstmember; said second -load positioning member having two projections forengaging the sides of a load; said projections being adjustable inposition along said second load positioning member, means for movingsaid arm on said rotatable member between an extended and retractedposition; said last named means including a lever extending from saidrst member; and actuating means fixed to the free end of said lever forrotating said lirst member.

References Cited in the ile of this patent UNITED STATES PATENTS2,613,831 Rees Oct. 14, 1952 2,780,422 Maglio Feb. 5, 1957 2,797,881Andrews July 2, 1957 2,843,337 Bennett Iuly l5, 1958 2,903,146 MeloySept. 8, 1959

